A combination gyrohorizon instrument for aircraft which visually indicates in addition to the dial display presentation of the instrument, by means of signal lamps appropriately placed with respect to the instrument dial and an audible signal indicative of energization of any one of the signal lamps, departures from straight and level flight that exceed reasonable limits of pitch and bank. The signal lamps, indicating "nose up," "nose down," "left wing down" and "right wing down" are in circuits energized by a first switching means controlled by the relative rotational position of the inner and outer gimbals of the instrument for sensing departure beyond reasonable safety limits in one direction or the other in the pitch axis, i.e., either "nose up" or "nose down" flight, and a second switch means controlled by the relative rotation position of the outer gimbal and the instrument casing for sensing departure beyond reasonable limits in the roll axis, i.e., either "left wing down" or "right wing down" flight.

As a method and device for representing the horizon on board an aircraft, there is displayed on the cathode tube of a collimator an image comprising a circle of small size inside which there are, on the one hand, a horizon line inclined to the horizontal by an angle equal to but opposite the rolling angle of the aircraft, the horizon line being remote from the center of the circle by a distance which is a function of the pitching angle in the upward direction when the aircraft is diving and in the downward direction when the aircraft is pulling the nose up, and which delimits to zones of different brightness and, on the other hand, a point representing a pole situated on the median line of the horizon line at a distance from the latter corresponding to a pitching angle of 90.degree.. A "head up" type control system is essentially provided.

The pilot or crew of an aircraft is alerted to the danger presented by wires in the vicinity of the aircraft by a flight instrument which includes a plurality of wire detected display elements, advantageously arranged as bars on the face of the flight instrument, and which display elements are color coded according to the level of danger presented to the aircraft by the detected wires.

An aircraft control position indicator is provided that displays the degree of deflection of the primary flight control surfaces and the manner in which the aircraft will respond. The display includes a vertical elevator dot/bar graph meter display for indicating whether the aircraft will pitch up or down, a horizontal aileron dot/bar graph meter display for indicating whether the aircraft will roll to the left or the right, and a horizontal rudder dot/bar graph meter display for indicating whether the aircraft will turn left or right. The vertical and horizontal display or displays intersect to form an up-down-left-right type display. Internal electronic display driver means receive signals from transducers measuring the control surface deflections and determine the position of the meter indicators one each dot/bar graph meter display. The device allows readability at a glance, easy visual perception in sunlight or shade, near-zero lag in displaying flight control position, and is not affected by gravitational or centrifugal forces.